JPH09317559A - Combustor for oxygen/methanol and its starting method - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a device and a starting method capable of eliminating a conventional malfunction, propelling space apparatuses aimed at a long time mission, and being used for a power system in relation to a combustor of oxygen/methanol, which is used for a thrustor, etc., of space apparatuses, and its starting method. SOLUTION: A combustor comprises an ignitor part 1 which sets the mixing ration of oxygen/methanol to 0.1 to 0.4 to ignite the mixture to burn it, main oxygen nozzles 17 which are formed integrally with the ignitor part and arranged at equal pitches on two circumferences concentrically arranged and differed from each other in the length of diameter, and an injector part 15 permitting oxygen and methanol from circumferentially and diametrically adjacent two main oxygen nozzles and two main methanol nozzles out of the main oxygen nozzles and the main methanol nozzles 20 to collide with each other at one point in a combustion chamber 14 to burn at a finally set mixing ratio. Thus, burnung of an ignition device 10 does not occur, stable ignition and combustion at a low mixing ratio are performed, and methanol less apt to vaporize is efficiently evaporated to realize highly efficient, stable final (steady) combustion.

Description

Detailed Description of the Invention

[0001]

TECHNICAL FIELD The present invention relates to the promotion of space equipment.
The present invention relates to a combustor for oxygen / methanol used for a power system or a propulsion / control system of a flying object that flies in outer space and generates a propulsive force or a driving force, and a starting method thereof.

[0002]

2. Description of the Related Art A propulsion device for space equipment for navigating in space, or an auxiliary power unit APU (Aux) in space equipment.
The motive power required for the propulsion device for the spacecraft such as the illiary Power Unit) or the spacecraft that fly in outer space, or the control device such as the side thruster applied for control is due to the combustion of the propellant composed of the oxidant and the fuel. The combustion energy obtained is used.

FIG. 8 is a sectional view showing a thruster injector conventionally used as a propulsion device for space equipment. In such an injector 01, dinitrogen tetraoxide N as an oxidizer is used.
TO (Nitrogen Tetraoxide N ₂
O ₄ ) is introduced from the oxidation manifold 02,
Monomethylhydrazine MMH as fuel (MonoM
Ethyl hydrazine CH ₃ NHNH ₂ )
Are introduced from the fuel manifold 03, and these self-igniting propellants NTO / MMH are combusted by mixing at the tip of the nozzle 04 to generate propulsion. The mixing ratio MR of these propellants NTO / MMH at the time of combustion is selected to be 1.65, and the mixing ratio is set to 1.65 which is the final set value from the time of starting the injector 01. Is jetted.

However, the propellant NTO / MMH used for such thrusters is highly toxic to both NTO and MMH, and requires careful handling. For example, when conducting a combustion test on the ground, after use, A great deal of effort must be given to the procedure. In addition, when the space equipment that uses thrusters that use such propellants is loaded and transferred to a carrier device that is carried by a crew member such as a ship, there may be cases where there is a safety problem for the crew member and the cargo cannot be transported. There is.

As an alternative to such defective propellants
And use a non-toxic propellant consisting of oxygen and hydrogen.
Some thrusters do so, but these propellants make up
Oxygen and hydrogen, which liquefy only at extremely low temperatures,
In order to mount it on space equipment etc. in a state, the volume is large,
The tank is too heavy to help achieve missions such as space equipment.
It will cause obstacles. Furthermore, a rocket strike from the ground
For raising, etc., liquid LO liquefied at extremely low temperature _Two, LH
_TwoIs used as a propellant,
Space for long-term missions and long-term missions
HOPE (H-II original pl
oxygen) when used for space equipment such as
Is LO_TwoAlthough it can be used in the state of
Hydrogen that is liquefied only at high temperature can keep the amount of evaporation small.
However, there is a problem that the mission cannot be achieved.
You.

[0006]

DISCLOSURE OF THE INVENTION The present invention uses oxygen / methanol as a propellant in order to solve the problems of the conventional propellants used in the above-mentioned propulsion devices for space equipment for navigating in outer space. In addition to adopting oxygen / methanol propellant, burn such propellant,
PROBLEM TO BE SOLVED: To provide a highly reliable oxygen / methanol combustor that can be stably used even in space equipment for navigating in outer space by solving the problems in the conventional combustor or the starting method, and its starting method. The task is to do.

[0007]

Therefore, the combustor for oxygen / methanol of the present invention has the following means. (1) Burns to generate thrust or driving force,
The mixing ratio of oxygen as an oxidant to methanol as a fuel is in the range of 0.1 to 0.4, more preferably,
An igniter unit capable of igniting with a low mixing ratio in the range of 0.16 to 0.34 and igniting with an igniter such as an exciter spark plug used in a conventional rocket engine to stably burn is provided. Provided. (2) A diameter centered on the igniter portion is provided on a wall surface that is provided in the vicinity of the igniter portion, is formed integrally with the igniter portion, and faces the combustion chamber that burns the propellant mixed with oxygen and methanol. A main oxygen injection hole and a main methanol injection hole are respectively arranged on two concentric circles having different lengths so as to be arranged on substantially the same diameter, and two main oxygen adjacent to each other on the same circle are arranged. 2 on the same diameter as the injection hole and the main oxygen injection hole
One main methanol injection hole, that is, two oxygen gas injection flows and two liquid methanol injection flows, which are respectively injected from four adjacent injection holes in the circumferential direction and the radial direction, are concentrated at one point. , So-called four-point liquid / gas collision between so-called oxygen gas and liquid methanol, and oxygen,
An injector portion was provided for causing combustion by setting the mixing ratio with methanol, the evaporation of which was promoted by the four-point liquid / gas collision, to the final set value.

The mixing ratio of oxygen / methanol in the igniter section and / or the injector section is changed from 0.1 to 0.4 at the time of ignition in the igniter section by changing the oxygen supply amount. It is preferable to increase the mixing ratio to the final set value in the injector section.

In the oxygen / methanol combustor of the present invention, the methanol used as a fuel has been found to be harmless from the literature, and since it burns in the air, it also burns with oxygen. As shown in Fig. 3, at a mixing ratio of 1.1 at which the oxygen / methanol specific thrust becomes maximum, 3000
It was previously predicted that the ignition device would burn out when the combustion temperature reached up to ° K, and the ignition was performed at this mixing ratio, but the region of the mixing ratio with oxygen for stable combustion is unknown. For this reason, a combustor in which the ignition device is ignited at a low combustion temperature mixing ratio without causing burnout of the ignition device has not been put into practical use until now.

For this reason, the inventor of the present invention uses a propellant that uses methanol as a fuel. Therefore, an exciter spark plug type thruster, which is used in a normal rocket engine, is manufactured, and oxygen / methanol having various mixing ratios is produced. As a result of conducting an ignition test of the propellant, a region where a stable ignition was clarified was clarified. Based on this test data, the mixing ratio of oxygen / methanol is in the range of 0.1 to 0.4, more preferably,
An igniter section for burning was provided at a low mixing ratio of 0.16 to 0.34.

As a result, at the time of starting the oxygen / methanol combustor, no explosion noise is generated, combustion can be stabilized, and a low mixing ratio prevents the ignition device from burning. The combustion temperature can be set to 1300 ° K or less, and the burning of the ignition device such as the exciter spark plug, which has been a problem in the normal oxygen / methanol combustor, can be prevented.

Further, as shown in Table 1, the mixing ratio is 0.4
It was confirmed by experiments by the inventor of the present application that explosion noise is generated and unstable combustion occurs in the above case. Therefore, ignition in the igniter section is performed at a low mixing ratio of 0.4 or less. As a result, the combustion at the time of ignition can be made stable and a highly reliable combustor can be obtained.

Further, the thrust of the combustor for oxygen / methanol according to the present invention, or the combustion at the time of supplying the driving force, in other words, the injector part which performs a steady operation is integrated with the igniter part, so that it is lightweight, It is suitable for application to space equipment and the like, which requires miniaturization. Further, since the liquid / gas is made to collide with four points and the oxygen gas and the methanol liquid are mixed, the evaporation of the liquid methanol which is ignited after the liquid is vaporized into the gas state is promoted, Compared to a normal oxygen / methanol combustor in which oxygen and methanol are mixed by simple injection or two-point collision, combustion is more stable and volume-efficient combustion can be performed. .

Further, the mixing ratio of oxygen / methanol can be set to a final setting value of about 1.1 which maximizes the thrust ratio regardless of the magnitude of the mixing ratio at the time of ignition so that combustion can be performed. Therefore, the operation with the maximum performance can be continuously performed, and the combustion efficiency can be improved.

Further, either the igniter section or the injector section,
Or by changing the oxygen supply to both,
The mixing ratio of oxygen / methanol is 0.1-0.4 at the time of ignition.
Since it is made possible to vary from 1 to the final set value in steady operation, for example, 1.1, combustion from ignition to steady operation can be made stable, and the heat load on the combustor can be reduced.

Further, the following means is adopted as the starting method of the oxygen / methanol combustor of the present invention. The weight mixing ratio of oxygen and methanol is 0.1 to 0.4, more preferably 0.1.
Mixing ratio for stable ignition in the range of 16 to 0.34, after ignition in the igniter section, the mixing ratio is the final set value, for example, about 1.1, liquid / gas four-point collision In order to make a smooth transition to combustion in the injector section, the oxygen supply amount in the ignited igniter section is gradually increased to gradually increase the mixing ratio, and the predetermined proportion of the injector section is set. The mixture ratio was set to 1.1 and the combustion in the injector section was switched to.

As a result, the ignition of oxygen / methanol at a combustion temperature of 3000 ° K is possible at a combustion temperature of 1300 ° K or less without the risk of burning of the igniter, and at the same time, the explosion noise at the time of ignition is generated. By avoiding this, stable combustion can be achieved. From the low mixing ratio at the time of ignition, for example, the performance of the propellant consisting of oxygen and methanol is maximized, and the mixing ratio of oxygen / methanol is 1.1, which is the final setting value.
The smooth transition of combustion of the oxygen / methanol propellant can be performed until the steady operation state is achieved, and rapid heat fluctuation of the combustor can be prevented, and the reliability can be made higher.

[0018]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of an oxygen / methanol combustor of the present invention will be described below with reference to the drawings.
FIG. 1 shows the first embodiment of the oxygen / methanol combustor of the present invention.
It is a longitudinal section showing a form.

As shown in the figure, the oxygen / methanol combustor according to the present embodiment comprises an igniter section 1 for ignition and a flow rate mixing during steady operation in which a mixing ratio for generating power is set to a final set value. It is integrally configured with the injector unit 15 set to the ratio. Of these, the igniter unit 1 introduces gaseous oxygen from the oxygen supply unit 3 via the igniter oxygen passage 4 and injects it from the igniter oxygen nozzle 6 into the igniter combustion zone 2 Liquid methanol is introduced from the injection manifold 5 and the methanol supply unit 7, and is similarly injected into the igniter combustion zone 2 into the igniter methanol injection manifold 7 and the igniter combustion zone 2 in which it is atomized by the igniter methanol nozzle 9. It consists of an exciter spark plug 10 that ignites by injecting a spark between the injected oxygen gas and atomized methanol between the anode 11 and the cathode 12.

Further, the oxygen injection manifold 5 for the igniter,
The oxygen gas flow rate measurement port and the methanol flow rate measurement port (not shown) are used to measure the flow rates of the oxygen gas and the methanol solution, which are introduced into the fuel injection manifold 8 for igniter and methanol, respectively, and to control the mixing ratio MR. Are provided in communication with the oxygen injection manifold 5 for the igniter and the methanol injection manifold for the igniter.

The igniter unit 1 of the oxygen / methanol combustor of the present embodiment is constructed as described above, and carries out the ignition of the propellant mixed with oxygen / methanol, and therefore is as follows.

First, when the power is generated by burning the oxygen / methanol propellant, when the oxygen / methanol weight flow rate ratio, that is, the mixing ratio MR is 1.1, the specific thrust, that is, the efficiency is maximum. , I know from the past.
Therefore, during steady operation by the injector unit 15 described later,
Combustion must be performed with this mixing ratio MR = 1.1. However, when oxygen / methanol propellant is combusted, as shown in FIG.
As shown in, the combustion temperature Tc changes abruptly as the oxygen / methanol mixture ratio MR changes. That is, as shown in FIG. 2, the mixing ratio MR = 1.1 that maximizes the efficiency.
It is known that the combustion temperature Tc at that time exceeds 3000 ° K.

Therefore, when ignition is performed at the mixing ratio MR which gives such a high combustion temperature Tc, the ignition device
For the material of the anode 11 of the exciter spark plug 10,
Usually, platinum-rhodium having a melting point of about 2000 ° K is used, so there is a concern that the anode 11 will be burned and restart will be impossible. Therefore, in order to avoid the peak of the combustion temperature Tc, the mixing ratio MR of oxygen / methanol when igniting in the igniter part 1 is higher than MR> 7 or low mixing ratio R <0.8. It is necessary to set the ratio side.

Further, as described above, oxygen supplied as an oxidant to the igniter unit 1 is supplied as a gas, whereas methanol supplied as a fuel is supplied as a liquid, so that ignition is performed. Even if it is atomized and injected into the igniter combustion zone 2 by the methanol nozzle 9 for a gas generator, it does not evaporate 100% immediately. From this, it can be seen that the mixing ratio MR of the igniter combustion zone 2 in the ignition state, which is controlled by the mixing ratio of evaporated methanol and gaseous oxygen, is higher than the set mixing ratio. For this reason, it is necessary to set the mixing ratio MR of the igniter combustion zone 2 at the time of ignition on the low mixing ratio side of MR <0.8, not on the high mixing ratio side of MR> 7.

For this purpose, the inventor of the present invention manufactured an exciter spark plug type thruster used in a normal rocket engine, and conducted a combustion test of oxygen / methanol propellant at various mixing ratios, particularly at low mixing ratios. As a result, the relationship between the mixing ratio MR and the combustion temperature Tc shown in FIG. 3 was grasped, and the stable ignition range shown in Table 1 was confirmed. That is, the combustion pressure Pc = 1 kg / cm after the combustion test
In the low mixing ratio range when ² a, as shown in FIG. 3,
It becomes a curve of the mixture ratio MR and the combustion temperature Tc, and a gentle range of this curve, that is, a gentle range of increase of the combustion temperature Tc with respect to the change of the mixture ratio MR, specifically, MR = 0.16 to. At 0.34, as shown in Table 1,
It was found that stable ignition could be obtained without making a loud noise.

From this, the relationship between the mixing ratio and the combustion temperature and the range where stable ignition is obtained at a high combustion pressure of the actual oxygen / methanol combustor Pc = 100 Kg / cm ² a were calculated. It is FIG. From the curve showing the relationship between the mixing ratio MR and the combustion temperature Tc in FIG. 4, the gradual range of the increase in the combustion temperature Tc with respect to the change in the mixing ratio MR is MR = 0.1 to 0.4. It is inferred from the comparison with FIG. 3 that stable ignition occurs in the low mixing ratio region of.

From the above, in the igniter unit 1 of the present embodiment, oxygen to be ejected from the igniter oxygen injection manifold 5 to the igniter combustion zone 2 through the igniter oxygen nozzle 6 and the igniter methanol injection manifold. 8 through the igniter methanol nozzle 9 into the igniter combustion zone.
The combustion temperature Tc is set to 1 to 0.4, more preferably 0.16 to 0.34, and stable ignition is possible without explosion noise, and the anode 11 is not burned. did.

Next, the mixing ratio MR of oxygen / methanol is
Set MR = 1.1, which maximizes the specific thrust, to the final setting value,
The injector unit 15 that performs steady operation will be described.

The injector section 15 introduces gaseous oxygen from the oxygen supply section 3 through the main oxygen injection passage 16 and injects it from the main oxygen injection hole 17 into the final combustion zone 18 for main oxygen injection manifold. 19, a main methanol injection hole 20 for injecting liquid methanol introduced into the igniter methanol injection manifold 8 into the final combustion zone 18.

In the final combustion zone 18, the main oxygen injection holes 17 for injecting oxygen and methanol, and the main methanol injection holes 21 are opened to the combustion chamber wall 13 as shown in FIG. There is. That is, FIG.
As shown in FIG. 3, the injector unit 15 formed in one body with the igniter unit 1 described above and arranged on the combustion chamber 14 side of the igniter unit 1 has a concentric circle shape centered on the igniter unit 1. Of 2
Of the two circumferences, the main oxygen opening 20 of the main oxygen injection hole 17 is provided on the outer circumference, and the main methanol opening 22 of the main methanol injection hole 21 is provided on the inner circumference. The main methanol openings 22 are arranged so as to correspond to each other on the same diameter in the diameter direction of the circumference.

Further, two main oxygen openings 20 provided on the outer circumference on two adjacent diameters and two main methanol openings 22 provided on the inner circumference, that is, in the circumferential direction and the radial direction. The main oxygen and the main methanol injected into the combustion chamber 14 from the four openings 20 and 22 provided adjacent to each other collide at one point in the combustion chamber 14, so-called liquid / gas four points. The main oxygen injection holes 17 and the main methanol injection holes 21 are arranged so as to collide with each other, burn, and form the final combustion zone 18. Since the gaseous oxygen and the liquid methanol are burned by this liquid / gas four-point collision method, the main methanol injection hole 2
Methanol, which is sprayed from No. 1 into the combustion chamber 14 and becomes a mist, has physical properties with large latent heat, but evaporation is promoted, and it easily transitions to a gaseous state in which combustion is performed, resulting in good combustion. Can be in a state. Further, by setting the oxygen / methanol mixing ratio MR of the injector 15 to 1.1, it is possible to perform combustion with a large specific thrust.

Further, in the oxygen / methanol combustor of this embodiment, the oxygen / methanol mixture ratio MR = 0.16 to 0.34 at the time of ignition by the igniter unit 1 and the injector unit 15 are used.
Mixing ratio MR = 1.1 in steady (final) operating state due to
Other mixing ratios are possible. That is, as described above, after igniting as a propellant having a mixing ratio of 0.16 to 0.34 of oxygen from the ignition oxygen nozzle 6 in the igniter section 1 and methanol from the igniter methanol nozzle 9 By injecting oxygen from the auxiliary oxygen injection hole 23 provided to inject oxygen into the combustion chamber 14 from the main oxygen injection manifold 19 shown in FIG. 1, the mixing ratio MR of oxygen / methanol is 0.5. .About.0.6 can be raised and the combustion zone also moves from the igniter combustion zone 2 to the intermediate combustion zone 24, which approaches the final combustion zone 18.

As a result, the combustion state of the low mixing ratio at the time of ignition is smoothly changed to the combustion state of the high mixing ratio at the time of steady operation.
It is possible to make a transition while continuing stable combustion. Further, this transition of the mixing ratio is caused by combustion at the time of ignition, and the liquid methanol injected from the methanol nozzle 9 for the eruptor is more easily vaporized, so that the combustion becomes unstable. Moreover, since the intermediate combustion zone 24 moves to a position away from the anode 11 where there is a risk of burning, the combustion temperature T increases due to the increase in the mixing ratio MR.
Even if c is increased to some extent, burning of the anode 11 is not caused.

Next, FIG. 6 is a vertical sectional view showing a second embodiment of the oxygen / methanol combustor of the present invention. The present embodiment shows application to the auxiliary power unit APU of space equipment.

As shown in the figure, a gas generator 30 for generating power by APU is constituted by an oxygen valve 31, a methanol valve 32, and the exciter spark plug 10 described above. An internal combustor is provided. Since the valve 32 for methanol has the same structure as the valve 31 for oxygen, the illustration thereof is omitted. Further, as shown in FIG. 7, the oxygen / methanol combustor that burns oxygen supplied from the oxygen valve 31 and methanol supplied from the methanol valve 32 is substantially the same as that shown in FIG. The structure is adopted.

However, in the oxygen / methanol combustor used in the APU shown in FIG. 7, the predetermined mixing ratio of oxygen / methanol when generating power is MR = 0.42, so the combustion zone is MR. = 0.16 to 0.34, and igniter combustion zone 2 in which igniter section 1 is ignited to burn.
Then, the predetermined MR is set to 0.4, and there are two final combustion zones 18 in which the injector portion 15 burns.

The combustion gas that has been burnt in the oxygen / methanol combustor and has flowed out of the gas generator 30 drives the turbine 33 and then vaporizes the liquid oxygen supplied from the liquid oxygen tank 34. 35 and liquid methanol supplied from the methanol tank are heated and exchanged by a heat exchanger (not shown), and then discharged to the outside. Further, the rotation of the turbine 33 is decelerated by the gear box 36 to drive the hydraulic pump 37 to generate power.

As in the present embodiment, the APU of space equipment
Since the oxygen used in the above is generally liquid and is mounted on the airframe, the liquid is gasified by the heat exchanger 35 and supplied to the gas generator. Further, the combustion gas generated in the gas generator 30 has a combustion temperature Tc of about 1200 ° K which is equal to or lower than the melting point of the turbine 33 so that the turbine 33 is not melted, and an oxygen / methanol mixture ratio MR of about 0.42. I usually choose.

[0039]

[Table 1]

[0040]

As described above, according to the oxygen / methanol combustor and the method of starting the same of the present invention, (1) at the time of starting the oxygen / methanol combustor, It is possible to make combustion stable without generating a roaring noise, and to prevent the ignition device such as an exciter spark plug from being burnt out by making the mixing ratio low so that the combustion temperature is 1300 ° K or less. (2) Further, since the thrust of the oxygen / methanol combustor or the combustion at the time of supplying the driving force, in other words, the injector part that performs the steady operation is integrated with the igniter part that ignites,
It is suitable for application to space equipment and the like, which are required to be lightweight and downsized. (3) In addition, the injector section that performs steady operation causes liquid / gas four-point collision to mix the oxygen gas and the methanol liquid at the mixing ratio of the final set value. The vaporization of liquid methanol, which is ignited after vaporized to a gas state, is promoted to stabilize the combustion, and the combustion with high volume efficiency can be achieved. (4) Further, the oxygen / methanol mixing ratio can be set to about 1.1, which is the maximum thrust ratio, and burned regardless of the magnitude of the mixing ratio at the time of ignition. You can continue to operate with maximum performance,
The combustion efficiency can be improved. (5) Further, since the mixing ratio of oxygen / methanol can be changed from the low mixing ratio at ignition to the mixing ratio in the steady operation state of the final set value that maximizes the performance of the oxygen / methanol propellant. A smooth transition of combustion can be performed, rapid heat fluctuations in the combustor can be prevented, and higher reliability can be achieved.

[Brief description of drawings]

FIG. 1 is a longitudinal sectional view showing a first embodiment of an oxygen / methanol combustor of the present invention,

FIG. 2 is a diagram showing a mixing ratio of oxygen / methanol and a combustion temperature;

FIG. 3 is a diagram showing an oxygen / methanol mixture ratio and a combustion temperature at a combustion pressure of 1 kg / cm ² a,

FIG. 4 is a diagram showing an oxygen / methanol mixture ratio and a combustion temperature at a combustion pressure of 100 kg / cm ² a,

5 is a schematic view of the oxygen / methanol combustor shown in FIG. 1, FIG. 5 (a) is a schematic vertical sectional view, and FIG. 5 (b) is an arrow A-A shown in FIG. 5 (a). Front schematic view in FIG.
FIG. 5C is a detailed vertical sectional partial schematic view showing the arrangement of the main oxygen injection holes and the main methanol injection in FIG.

FIG. 6 is a second implementation of the oxygen / methanol combustor of the present invention.
Longitudinal sectional view showing the form,

FIG. 7 is a vertical sectional view showing details of the oxygen / methanol combustor shown in FIG. 6;

FIG. 8 is a cross-sectional view of an injector used in the thrust of conventional space equipment.

[Explanation of symbols]

 1 Ignition unit 2 Ignition combustion zone 3 Oxygen supply unit 4 Oxygen passage for igniter 5 Oxygen injection manifold for igniter 6 Oxygen nozzle for igniter 7 Methanol supply unit 8 Methanol injection manifold for igniter 9 Methanol nozzle for igniter 10 Exciter spark plug 11 Anode 12 cathode 13 combustion chamber wall 14 combustion chamber 15 injector part 16 main oxygen injection passageway 17 main oxygen injection hole 18 final combustion zone 19 main oxygen injection manifold 20 main oxygen opening 21 main methanol injection hole 22 main methanol opening 23 auxiliary oxygen Injection hole 24 Intermediate combustion zone 30 Gas generator 31 Valve for oxygen 32 Valve for methanol 33 Turbine 34 Liquid oxygen tank 35 Heat exchanger (for liquid oxygen)

Claims (2)

[Claims] 1. In an oxygen / methanol combustor that combusts supplied oxygen and methanol to generate thrust or driving force, the mixing ratio of the oxygen to the methanol is set to 0.1 to 0.4. And an igniter portion for performing combustion, and a main oxygen injection hole and a main methanol injection hole that are formed integrally with the igniter portion and are arranged at equal pitches on two concentrically arranged circles. Liquid / gas four-point collision, in which the oxygen and the methanol are concentrated at one point, which are injected from the main oxygen injection hole and the main methanol injection hole, which are arranged adjacent to each other in the circumferential direction and the radial direction, respectively. And an injector part for performing combustion with the mixing ratio set to a final set value. 2. The method for starting an oxygen / methanol combustor according to claim 1, wherein the mixing ratio of oxygen and methanol is 0.1.
After igniting in the igniter section at a value of up to 0.4, the amount of oxygen supply is increased to perform combustion in which the mixing ratio is gradually increased, and then the mixing ratio is set to a final set value, and the liquid / gas is set. A method for starting a combustor for oxygen / methanol, characterized by transitioning to combustion in an injector part, which performs combustion by four-point collision.